WORTMANN FX 77-080 (fx77080-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 77-080 (fx77080-il) Reynolds number: 50,000 Max Cl/Cd: 23.88 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx77080-il-50000-n5.txt Download as CSV file: xf-fx77080-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 77-080
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6948 0.09326 0.08590 -0.0059 1.0000 0.0553
-10.000 -0.7080 0.08531 0.07801 -0.0112 1.0000 0.0548
-9.750 -0.7283 0.07690 0.06962 -0.0176 1.0000 0.0540
-9.500 -0.7536 0.07037 0.06304 -0.0208 1.0000 0.0534
-9.250 -0.7744 0.06496 0.05749 -0.0215 1.0000 0.0532
-9.000 -0.7885 0.05980 0.05208 -0.0216 1.0000 0.0531
-8.750 -0.7962 0.05503 0.04698 -0.0210 1.0000 0.0536
-8.500 -0.7980 0.05071 0.04223 -0.0199 1.0000 0.0550
-8.250 -0.7962 0.04653 0.03749 -0.0185 1.0000 0.0571
-8.000 -0.7887 0.04291 0.03333 -0.0170 1.0000 0.0596
-7.750 -0.7736 0.04071 0.03103 -0.0159 1.0000 0.0625
-7.500 -0.7582 0.03807 0.02804 -0.0146 1.0000 0.0653
-7.250 -0.7413 0.03546 0.02487 -0.0132 1.0000 0.0701
-7.000 -0.7227 0.03374 0.02308 -0.0121 1.0000 0.0754
-6.750 -0.7024 0.03179 0.02082 -0.0109 1.0000 0.0817
-6.500 -0.6820 0.03023 0.01916 -0.0097 1.0000 0.0892
-6.250 -0.6607 0.02874 0.01747 -0.0086 1.0000 0.0997
-6.000 -0.6385 0.02734 0.01585 -0.0074 1.0000 0.1116
-5.750 -0.6177 0.02619 0.01472 -0.0063 1.0000 0.1275
-5.500 -0.5963 0.02506 0.01358 -0.0052 1.0000 0.1460
-5.250 -0.5745 0.02406 0.01252 -0.0041 1.0000 0.1698
-5.000 -0.5531 0.02316 0.01166 -0.0031 1.0000 0.1949
-4.750 -0.5312 0.02231 0.01083 -0.0021 1.0000 0.2219
-4.500 -0.5088 0.02149 0.01006 -0.0011 1.0000 0.2510
-4.250 -0.4863 0.02070 0.00934 -0.0002 1.0000 0.2831
-4.000 -0.4641 0.01989 0.00869 0.0008 1.0000 0.3201
-3.750 -0.4436 0.01912 0.00808 0.0022 1.0000 0.3649
-3.500 -0.4243 0.01836 0.00760 0.0039 1.0000 0.4228
-3.250 -0.4058 0.01762 0.00724 0.0061 1.0000 0.4962
-3.000 -0.3869 0.01699 0.00700 0.0085 1.0000 0.5824
-2.750 -0.3646 0.01654 0.00688 0.0107 1.0000 0.6769
-2.500 -0.3331 0.01635 0.00688 0.0116 1.0000 0.7680
-2.250 -0.2904 0.01637 0.00688 0.0101 1.0000 0.8456
-2.000 -0.2390 0.01646 0.00679 0.0066 1.0000 0.9057
-1.750 -0.1737 0.01655 0.00664 -0.0002 1.0000 0.9527
-1.500 -0.1038 0.01644 0.00630 -0.0086 1.0000 0.9901
-1.250 -0.0724 0.01623 0.00597 -0.0101 1.0000 1.0000
-1.000 -0.0583 0.01606 0.00574 -0.0081 1.0000 1.0000
-0.750 -0.0441 0.01592 0.00557 -0.0061 1.0000 1.0000
-0.500 -0.0296 0.01583 0.00545 -0.0040 1.0000 1.0000
-0.250 -0.0148 0.01578 0.00538 -0.0020 1.0000 1.0000
0.000 0.0000 0.01576 0.00536 0.0000 1.0000 1.0000
0.250 0.0149 0.01578 0.00538 0.0020 1.0000 1.0000
0.500 0.0296 0.01583 0.00545 0.0041 1.0000 1.0000
0.750 0.0442 0.01592 0.00557 0.0061 1.0000 1.0000
1.000 0.0584 0.01606 0.00574 0.0081 1.0000 1.0000
1.250 0.0725 0.01623 0.00596 0.0101 1.0000 1.0000
1.500 0.1033 0.01643 0.00628 0.0087 0.9903 1.0000
1.750 0.1743 0.01654 0.00663 0.0001 0.9523 1.0000
2.000 0.2397 0.01646 0.00680 -0.0066 0.9049 1.0000
2.250 0.2902 0.01637 0.00687 -0.0101 0.8460 1.0000
2.500 0.3331 0.01635 0.00688 -0.0116 0.7685 1.0000
2.750 0.3646 0.01654 0.00687 -0.0107 0.6757 1.0000
3.000 0.3869 0.01700 0.00700 -0.0085 0.5813 1.0000
3.250 0.4058 0.01763 0.00723 -0.0060 0.4955 1.0000
3.500 0.4242 0.01836 0.00760 -0.0039 0.4222 1.0000
3.750 0.4437 0.01912 0.00812 -0.0022 0.3649 1.0000
4.000 0.4640 0.01990 0.00868 -0.0008 0.3197 1.0000
4.250 0.4863 0.02070 0.00934 0.0002 0.2827 1.0000
4.500 0.5088 0.02150 0.01007 0.0011 0.2510 1.0000
4.750 0.5312 0.02231 0.01083 0.0021 0.2217 1.0000
5.000 0.5531 0.02316 0.01167 0.0031 0.1949 1.0000
5.250 0.5745 0.02407 0.01253 0.0041 0.1698 1.0000
5.500 0.5963 0.02507 0.01360 0.0052 0.1461 1.0000
5.750 0.6177 0.02620 0.01472 0.0063 0.1275 1.0000
6.000 0.6386 0.02734 0.01586 0.0074 0.1116 1.0000
6.250 0.6606 0.02873 0.01746 0.0086 0.0996 1.0000
6.500 0.6818 0.03018 0.01910 0.0097 0.0888 1.0000
6.750 0.7024 0.03180 0.02083 0.0109 0.0816 1.0000
7.000 0.7227 0.03375 0.02309 0.0121 0.0754 1.0000
7.250 0.7412 0.03549 0.02491 0.0132 0.0699 1.0000
7.500 0.7581 0.03808 0.02806 0.0146 0.0652 1.0000
7.750 0.7736 0.04072 0.03103 0.0159 0.0624 1.0000
8.000 0.7890 0.04278 0.03313 0.0170 0.0592 1.0000
8.250 0.7958 0.04658 0.03755 0.0185 0.0568 1.0000
8.500 0.7980 0.05071 0.04223 0.0199 0.0548 1.0000
8.750 0.7961 0.05507 0.04701 0.0210 0.0535 1.0000
9.000 0.7883 0.05986 0.05215 0.0216 0.0531 1.0000
9.250 0.7737 0.06510 0.05763 0.0215 0.0530 1.0000
9.500 0.7530 0.07050 0.06319 0.0207 0.0534 1.0000
9.750 0.7286 0.07692 0.06964 0.0175 0.0540 1.0000
10.000 0.7078 0.08551 0.07821 0.0109 0.0547 1.0000
10.250 0.6954 0.09330 0.08594 0.0058 0.0553 1.0000
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